Mainline Aircraft Wing-to-Fuselage Coupling Structure Topological Optimization Method Evolution

Aeronautical and Space-Rocket Engineering


Аuthors

Boldyrev A. V.*, Zolotov D. V.**

Samara National Research University named after Academician S.P. Korolev, Moskovskoe shosse, 34, Samara, Russia

*e-mail: boldirev.av@ssau.ru
**e-mail: dmitriy.zolotov98@mail.ru

Abstract

The authors suggested a topological optimization method of the wing-to-fuselage coupling structure with account for both strength and weight efficiency requirements
The design object is an elastic thin-walled system that ensures the normal forces transfer from the detachable wing parts to the self-balancing at the central zone of the fuselage. The shearing forces from the wing are being balanced on the fuselage skin. The the sealed fuselage framed shell takes up as well the excessive internal pressure, bending and torsion of the fuselage.
A special criterion, namely the “power factor coefficient”, accounting for the value and stretch of the internal forcings transfer in the structure, is being used as the goal function.
The suggested topological optimization method employs a combined finite element model (FEM), which consists of a set of FEMs of three types. The FEM of the first type (FEM-1) is intended to determine the number, type and location of structural elements that ensure rational wing-to-fuselage coupling. For the topological optimization execution, the permissiible geometric area,  inside which the sought-for elements of the copling structure may be located, is being filled by the hypothetically continuous elastic medium of variable density and stiffness. The FEM of the second type (FEM-2) is intended for topological optimization of the thin-walled elements of an object such variable cross-section beams, reinforced panels, ribs, frames. This model incorporates various thickness shells inscribed into the structure geometric restrictions. A FEM of the third type (FEM-3) includes structural elements, which are defined in the design process of the load bearing scheme of the structure. Rod, plate, and solid finite elements are being used for their modeling. 
The article adduces a numerical example of the fuselage compartment design process in wing-to-fuselage coupling zone, demonstrating the suggested topological optimization method operability. The cylindrical fuselage compartment in the zone of its coupling with the low-lying wing was selected as the object of research. The detachable wing parts are being formed by the Nyu/Grumman K-1 supercritical profile with a relative thickness of 12%. A new technical solution based on the  system of various cross-section beams which weight is 18.6% lower relative to the power scheme of the structure with centre-section wing with effective construction depth.
Keywords: center section structural arrangement, combined wing-to-fuselage coupling model, variable density body, variable thickness plate, variable cross-section beam, structure weight efficiency

Keywords:

center section structural arrangement, combined wing-to-fuselage coupling model, variable density body, variable thickness plate, variable cross-section beam, structure weight efficiency

References

  1.  Dmitriev VG. (ed) Problems of creating promising aerospace technology. Moscow: Fizmatlit; 2005. 648 p. (In Russ.). 
  2.  Pogosyan MA, Liseitsev NК, Ryabov VA. Evolution of scientific foundations for aircraft design and problems of personal training. Aerospace MAI Journal. 2005;12(2):5-9. (In Russ.). URL: https://vestnikmai.ru/eng/publications.php?ID=7970
  3.  Komarov VA. Designing power circuits of aircraft structures. In: Actual problems of aviation science and technology. Moscow: Mashinostroenie; 1984. p. 114-129. (In Russ.).
  4.  Bendsoe MP, Kikuchi N. Generating optimal topologies in structural design using a homogenization method. Computer Methods in Applied Mechanics and Engineering. 1988;71(2):197-224. DOI: 10.1016/0045-7825(88)90086-2
  5.  Eschenauer HA, Olhoff N. Topology optimization of continuum structures: A review. Applied Mechanics Reviews. 2001;54(4):331-389. DOI: 10.1115/1.1388075
  6.  Rozvany GIN. A critical review of established methods of structural topology optimization. Structural and Multidisciplinary Optimization. 2009;37(3):217-237. DOI: 10.1007/s00158-007-0217-0
  7.  Zhu JH, Zhang WH, Xia L. Topology optimization in aircraft and aerospace structures design. Archives of Computational Methods in Engineering. 2016;23(4):595-622. DOI: 10.1007/s11831-015-9151-2
  8.  Lógó J, Ismail H. Milestones in the 150-year history of topology optimization: A review. Computer Assisted Methods in Engineering and Science. 2020;27(2–3):97-132. URL: https://doi.org/10.24423/cames.296.
  9.  Lipin EK, Chedrik VV. Application of optimality criteria for solving the problem of optimizing structures under stress and displacement constraints. Uchenye zapiski TsAGI. 1989;XX(4):73−83. (In Russ.). EDN MQIITL
  10.  Nikiforov AK, Chedrik VV. On methods and algorithms of multidisciplinary optimization of power structures. Uchenye zapiski TsAGI. 2007;XXXVIII(1−2):129-143. (In Russ.). EDN JWVOAN
  11.  Penkov EA. Automation of complicated structural and power circuit development. Polet. Obshcherossiiskii nauchno-tekhnicheskii zhurnal. 2007(1):40-48. (In Russ.). EDN HZIWPH
  12.  Boldyrev AV. Wing structural optimization under strength and stiffness constrains. Aerospace MAI Journal. 2009;16(3):15-21. (In Russ.). URL: https://vestnikmai.ru/eng/publications.php?ID=10340
  13.  Schuhmacher G, Stettner M, Zotemantel R, et al. Optimization assisted structural design of a new military transport aircraft. 10th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference (August 30 − September 1 2004; Albany, New York). p. 3803−3811. DOI: 10.2514/6.2004-4641
  14.  Seeger J, Wolf K. Structural optimization of composite aircraft panels with large cut-outs. European Conference on Materials and Structures in Aerospace (May 26-27, 2008; Berlin, Germany). p. 19-27.
  15.  Boldyrev AV, Pavel’chuk MV, Sinel’nikova RN. Enhancement of the fuselage structure topological optimization technique in the large cutout zone. Aerospace MAI Journal. 2019;26(3):62-71. (In Russ.). URL: https://vestnikmai.ru/eng/publications.php?ID=10747
  16.  Niu MCY. Airframe Structural Design. Practical Design Information and Data on Aircraft Structures. 2nd ed. Hong Kong: Adaso Adastra Engineering Center; 2011. 611 p.
  17.  Boldyrev AV, Zolotov DV. Evaluation of mainline aircraft center section weight efficiency. Vestnik of Samara University. Aerospace and Mechanical Engineering. 2025;24(1):7-18. (In Russ.). DOI: 10.18287/2541-7533-2025-24-1-7-18
  18.  Komarov AA. Fundamentals of designing power structures. Kuibyshev: Knizhnoe izdatel'stvo; 1965. 88 p. (In Russ.).
  19.  Komarov VA. Weight analysis of aircraft structures: theoretical foundations. Polet. Obshcherossiiskii nauchno-tekhnicheskii zhurnal. 2000(1):31–39. (In Russ.). EDN TEHETV
  20.  Semenov VN. Designs of aircraft of closed and variable circuits. Moscow: TsAGI; 2006. 227 p. (In Russ.).
  21.  Gumenyuk AV. Forecasting and mass control of aircraft structures using the criterion “force factor”. PhD thesis. Samara State Aerospace University named after SP. Korolev; 2004. 189 p. (In Russ.).
  22.  Soenarjo MA. Aircraft wing box joint. Patent US20130062467A1, 14.04.2015.
  23.  Rychkov SP. Modeling of structures in the Femap environment with NX Nastran. Moscow: DMK Press; 2013. 784 p. (In Russ.).
  24.  Boldyrev AV, Zolotov DV, Kishov EA. A program for obtaining an equal-strength material distribution in combined elastic systems. Certificate of state registration of a computer program RU2025612034, 24.01.2025. (In Russ.).
  25.  Boldyrev AV, Zolotov DV, Shilimov KG. Wing and fuselage connection. Patent RU2841722C1, 16.06.2025. (In Russ.).

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